Thermoplastic resin composite and method of preparing the same

ABSTRACT

Disclosed is a resin composite having improved tensile properties and a method of preparing the same. Particularly, the resin composite comprises a matrix resin and a reinforcement resin which are made of thermoplastic resin compositions.

CROSS-REFERENCE TO RELATED APPLICATION

This application is a divisional application of U.S. application Ser.No. 14/922,683, filed Oct. 26, 2015, which claims the benefit ofpriority to Korean Patent Application No. 10-2015-0092448 filed with theKorean Intellectual Property Office on Jun. 29, 2015, the entirecontents of which are incorporated herein by reference.

TECHNICAL FIELD

The present invention relates to a thermoplastic resin composite and amethod of preparing the same, and more particularly. In particular, thethermoplastic resin composite may be a self-reinforced thereby havingimproved physical properties.

BACKGROUND

Fiber reinforced plastics (FRPs) have been widely used as compositematerials in various fields, for example, civil engineering andarchitectural fields, a transportation field, electronic device fields,aviation and aerospace fields, and the like. The thermosetting resinsuch as an unsaturated polyester resin, a vinyl ester resin, an epoxyresin, a phenol resin, or the like, or a thermoplastic resin such aspolyethylene, polypropylene, an acrylonitrile-butadiene-styrene (ABS)resin, polycarbonate, polyacetal, polyamide, polystyrene, polyphenylenesulfide, or the like has been used as a matrix resin in the FRP, and aninorganic fiber such as a glass fiber, a metal fiber, a ceramics fiber,a carbon fiber, or the like, or an organic fiber such as a naturalfiber, a polypropylene fiber, a polyamide fiber, a polyester fiber, apolyacrylate fiber, a polyimide fiber, or the like have been used invarious forms as a reinforcement fiber. Among these reinforcementmaterials, particularly, the glass fiber has been mainly used.

Generally, the FRP includes a resin matrix and a reinforcement materialwhich are made of different materials. For example, a FRP using theinorganic fiber such as the glass fiber or the like, or a FRP using anorganic fiber made of a different material from that of the resin matrixmay have a disadvantage in recyclability of FRP. Therefore, a FRPincluding the resin matrix and the reinforcement materials which aremade of similar compositions, such as thermosetting or thermoplasticpolymer resins, and having excellent recyclability has been developed.

In the related arts, an exemplary method of preparing a FRP includingthe same resin matrix and reinforcement material, the reinforcementmaterial with a high strength and high elasticity fiber or film made ofa thermoplastic resin, or the matrix resin which is the samethermoplastic resin as the reinforcement material can be dissolved in anorganic solvent, heated and compacted to form a composite. However,since the method uses the solvent, it may cause an environmentalcontamination. Therefore, a method being capable of simple and efficientmethod of preparing a FRP having high strength and excellentrecyclability has been demanded without generating a negativeenvironmental influence.

For instance, JP Patent No. 3,130,288B discloses a method of obtaining astretched isotactic polypropylene fiber having a high strength, lowelongation, high Young's modulus, high melting point, and low thermalshrinkage ratio, by stretching a crystalline polypropylene fiber at ahigh stretch ratio under pressurized saturated steam of 0.20 Mpa ormore.

Further, U.S. Pat. No. 8,052,913B discloses a simple and efficientmethod of preparing a polyolefin resin mold reinforced with apolypropylene-based fiber, which has a high strength and excellentrecyclability and can be applied to various uses. Specifically, themethod includes compacting step of a ply laminating an unstretchedmatrix layer having a low melting point as an intermediate layer betweenstretched polymer reinforcement materials under a specific time,temperature and pressure conditions, and cooling the compacted ply. Thecompacting process is preferably performed at a pressure of 10 MPa orless, and may be performed using a double belt press, or the like.

The physical properties of the resin composite manufactured by theabove-mentioned documents depending on a compaction temperature areshown in FIG. 1.

Further, in the disclosure of U.S. Pat. No. 8,021,592, an assemblycomposed of two or more stretched webs made of polypropylene having aspecific melting point, a recrystallization temperature, and a molecularweight is treated and compacted at elevated temperature and pressureconditions being sufficient to partially melt polypropylene, and cooledat a temperature lower than the recrystallization temperature and anelevated pressure condition, at a cooling rate of 35° C./minutes orhigher. The tensile properties of the composite depending on a coolingcondition of the resin composite at the time of compact molding areillustrated in FIG. 2.

In the methods disclosed in above U.S. Pat. Nos. 8,052,913 and8,021,592, a batch-type heating and compaction method using a hot pressis used to prepare a self-reinforced composite, however, the batch-typedand discontinuous methods using hot press equipment may deteriorateproductivity.

Therefore, a FRP composed of the same materials of matrix resin and areinforcement resin and a method of preparing the same for achievinghigh productivity in a continuous process, have been still required.

SUMMARY OF THE INVENTION

In preferred aspects, the present invention provides a resin compositethat can be used as FRPs, and a method of preparing the same. Inparticular, the resin composition may comprise a matrix resin and areinforcement resin which are made from polymeric resins such asthermoplastic resin, as such the those materials can be recycled withoutseparating polymeric materials from the inorganic materials.

In one aspect, provided is a method of preparing a resin composite.

The method may comprise: melting a reinforcement resin and a matrixresin; and impregnating the reinforcement resin into the matrix resin toform the resin composite.

The resin composite may be prepared using a double belt press laminatorwhich may be divided into at least sections. Particularly, a firstsection of the double belt press laminator may be located closest to aresin injection part of the laminator and a second section of the doublebelt press laminator may be located next to the first section,

Preferably, a temperature in the double belt press laminator maydecrease from the resin injection part to a resin discharge part of thelaminator.

In particular, a temperature of the first section (T₁) may be in a rangeof about (T_(m)−5)° C. to (T_(m)+5)° C. as T_(m) being a meltingtemperature of the reinforcement resin.

Preferably, the resin composition may be prepared in continuous processusing the double belt press laminator.

The method may further comprise recrystallizing the formed resincomposite in the second section. In particular, a temperature of thesecond section (T₂) may be in a range of about (T_(m)−70)° C. to(T_(m)−50)° C. as T_(m) being a melting temperature of the reinforcementresin.

Preferably, the temperature of the second section (T₂) may be lowered byusing a cooling apparatus positioned between the first and secondsections, and the cooling apparatus is installed between the first andsecond sections.

The method may further comprise laminating the matrix resin and thereinforcement resin before the melting the reinforcement resin and thematrix resin.

The double belt press laminator may comprise four or more sectionshaving different temperature conditions. The first section of suchdouble belt press laminator may be located closest to the resininjection part of the laminator and the second section, the third andthe fourth sections may be located sequentially from the first sectionto the resin discharge part.

Preferably, the temperature of the second section (T₂) may be in a rangeof about (T_(m)−70)° C. to (T_(m)−50)° C., a temperature of the thirdsection (T₃) may be in a range of about (T_(m)−90)° C. to (T_(m)−80)°C., and a temperature of the fourth section (T₄) may be in a range ofabout (T_(m)−110)° C. to (T_(m)−90)° C., as T_(m) being a meltingtemperature of the reinforcement resin.

Preferably, a ratio of an interval between the double belts of laminatorto a thickness of the laminated matrix resin and the reinforcement resinmay range from about 0.75 to about 0.95.

Preferably, the matrix resin may be in a form of a film, and thereinforcement resin may be in a form of a fiber or fabric.

Preferably, the matrix resin and the reinforcement resin may have amelting temperature of about 130 to 165° C.

The matrix resin and the reinforcement resin may be thermoplastic resincomprising at least one selected from the group consisting ofpolyethylene, polypropylene, an acrylonitrile-butadiene-styrene (ABS)resin, polycarbonate, polyacetal, polyamide, polystyrene, andpolyphenylene sulfide. Alternatively, the matrix resin and thereinforcement resin may be polyolefin resin.

The double belt press laminator may include each the first and secondsection of the laminator which is driven by a separate roller, or whenthe double belt press laminator comprises four or more of dividedsections, each section of the laminator may be driven by a separateroller.

The resin composite as prepared by the above described method may havespecific gravity of about 0.880 to 0.900, a tensile strength of about0.80 to 1.10, and a tensile modulus of about 0.80 to 1.1.

Further provided is a resin composite prepared using the method asdescribed herein.

Other aspects of the present invention are disclosed infra.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 illustrates the physical properties of a thermoplastic resincomposite depending on a compression temperature of the resin compositeprepared by a conventional method.

FIG. 2 illustrates the tensile properties of a thermoplastic resincomposite depending on a cooling condition of the resin compositeprepared by a conventional method.

FIG. 3 illustrates an exemplary internal sections of an exemplary doublebelt press laminator used in an exemplary embodiment of the presentinvention.

FIG. 4 is a graph showing changes in physical properties of an exemplaryresin composite depending on compression temperature in an exemplaryembodiment of the present invention.

FIG. 5 is a graph showing changes in physical properties of an exemplaryresin composite obtained by applying the recrystallization process in anexemplary embodiment of the present invention.

FIG. 6 is a DSC graph showing changes in melting point of exemplaryresin composites obtained in an exemplary embodiment of the presentinvention.

FIG. 7 illustrates a main crystalline structure of polypropylene in anexemplary embodiment of the present invention.

FIG. 8 illustrates exemplary configurations of polypropylene ofexemplary resin composites obtained from XRD patterns in an exemplaryembodiment of the present invention.

DETAILED DESCRIPTION

The terminology used herein is for the purpose of describing particularexemplary embodiments only and is not intended to be limiting of theinvention. As used herein, the singular forms “a”, “an” and “the” areintended to include the plural forms as well, unless the context clearlyindicates otherwise. It will be further understood that the terms“comprises” and/or “comprising,” when used in this specification,specify the presence of stated features, integers, steps, operations,elements, and/or components, but do not preclude the presence oraddition of one or more other features, integers, steps, operations,elements, components, and/or groups thereof. As used herein, the term“and/or” includes any and all combinations of one or more of theassociated listed items.

Unless specifically stated or obvious from context, as used herein, theterm “about” is understood as within a range of normal tolerance in theart, for example within 2 standard deviations of the mean. “About” canbe understood as within 10%, 9%, 8%, 7%, 6%, 5%, 4%, 3%, 2%, 1%, 0.5%,0.1%, 0.05%, or 0.01% of the stated value. Unless otherwise clear fromthe context, all numerical values provided herein are modified by theterm “about.”

Hereinafter, a resin composite and a method for manufacturing the sameaccording to various exemplary embodiments will be explained in detail.

In one aspect, the present invention provides a resin composite havingimproved tensile properties, and the resin composite may comprise amatrix resin and a reinforcement resin. In particular, the matrix resinand the reinforcement resin may have same composition. In certainaspect, the resin composite of the present invention may comprise athermoplastic resin composite, and be a self-reinforced resin composite.

In another aspect, the present invention provides a method of preparingthe above resin composite having improved tensile properties bycontrolling the process conditions such as a temperature, a pressure,and the like of each process.

An exemplary embodiment of the present invention provides aself-reinforced thermoplastic resin composite having improved tensileproperties, and a method of preparing the same.

In addition, an exemplary embodiment of the present invention provides amethod of preparing a thermoplastic resin composite using a double-beltpress laminator, instead of a batch-typed discontinuous process, bycontrolling the process parameters and the optimal properties of aself-reinforced composite. In particular, the method may be performed incontinuous process. Thus, the method of present invention can achieve animprovement in the physical properties and the productivity.

In an exemplary embodiment, a self-reinforced thermoplastic compositemay be prepared by using a double belt laminator with a higherproductivity than the compression molding. In the related arts, thecompression cooling process may be required for performing arecrystallization step after a melting step of thermoplastic resin.Thus, the temperature can be controlled to be suitable for each sectionof double-belt laminator, so as to produce the self-reinforced compositewith excellent properties.

A conventional laminating method using a double-belt laminator has beenused largely for preparing the thermoplastic prepreg. The prepreg is asheet-type product used as an intermediate material for producing themolded composite which may be prepared by using the matrix resinimpregnated into the reinforcement fiber beforehand.

As illustrated in FIG. 3, a double-belt typed heating/pressing apparatusmay continuously apply the heat and the pressure on the thermoplasticprepreg by using a continuous metal belt positioned at upper and lowerparts of the thermoplastic pregreg. The heating/pressing apparatus withdouble belt press type may be mainly used in a continuous process.

The thermoplastic resin composite including the same thermoplastic resincomposition of matrix resin and a reinforcement resin may have adifferent thermal stability from a thermoplastic prepreg which includesa carbon/glass fiber as a reinforcement material in the conventionalart. Further, in a manufacturing process, the resin composite of thepresent invention may require a suitable temperature condition forpreventing the physical properties from being deteriorated due to theheat shrinkage of the thermoplastic reinforcement material. Therefore,in the case that the conventional heating/pressing apparatus in doublebelt type and the manufacturing conditions applied for the prepregpreparation are used for the thermoplastic resin composite of thepresent invention, the physical properties of the reinforcement resinmay be deteriorated due to shrinkage and melting of the reinforcementresin caused by heat.

Accordingly, the method of preparing a resin composite according to anexemplary embodiment of the present invention may include melting areinforcement resin and a matrix resin, and impregnating thereinforcement resin into the matrix resin. Preferably, the method mayfurther include a recrystallizing step of the impregnated resincomposite. In addition, before the melting and impregnating, the methodmay further include a laminating step of the matrix resin and thereinforcement resin.

In the melting and impregnating steps, the laminated resins used forpreparing the resin composite may be injected into inside of double beltlaminator and the reinforcement resin may be melted and thus impregnatedinto the matrix resin by being applied with heat and pressure.

As used herein, the term, “a reinforcement material for self-reinforcedresin composite” means a resin in a broad meaning, and is distinguishedfrom an inorganic fiber such as carbon fiber, glass fiber, and the like,as a reinforcement material in related art. In a preferred aspect, thereinforcement material for self-reinforced resin composite means a resinwhich has the same or similar physical properties of a matrix resin. Forexample, the self-reinforced property of reinforcement material may bedetermined by differential scanning calorimetry (DSC). When thecomposite made from the same resin composition of matrix andreinforcement material is analyzed by DSC analysis, the“self-reinforced” material may mean the materials characterized by asingle melting temperature (T_(m)) peak at a primary heating peak,instead of two different peaks.

In the present invention, as the matrix resin and the reinforcementresin, all of the thermoplastic resin known in the art may be used, butare not particularly limited.

In an exemplary embodiment of the present invention, the matrix resinmay be in a form of a film, and the reinforcement resin may be in a formof a fiber or fabric. The matrix resin and the reinforcement resin maybe thermoplastic resins having a melting temperature of about 130 to165° C.

The examples of the self-reinforced material can include a thermosettingresin such as an unsaturated polyester resin, a vinyl ester resin, anepoxy resin, a phenol resin or the like, and a thermoplastic resin suchas polyethylene, polypropylene, an acrylonitrile-butadiene-styrene (ABS)resin, polycarbonate, polyacetal, polyamide, polystyrene, polyphenylenesulfide or the like. The reinforcement resin, as used herein, may be aresin having physical properties equal or similar to those of the matrixresin. The matrix resin and the reinforcement resin may be polyolefinresins such as homopolymers, heteropolymers, or copolymers including analiphatic olefin having a C2 to C4 a repeating unit. Examples of thepolyolefin resin may include polyethylene, polypropylene, a copolymer ofpolyethylene and polypropylene, and the like.

The method of preparing a resin composite according to an exemplaryembodiment of the present invention may include, by using a double beltpress laminator divided into at least two different temperaturesections: melting the reinforcement resin and the matrix resin; andimpregnating the reinforcement resin into the matrix resin. Accordingly,at least two sections, for example, a first section and a secondsection, may be arranged sequentially from a resin injection part of thelaminator to a resin discharge part thereof, and those sections may havea temperature gradient that is decreasing from the resin injection partof the laminator to the resin discharge part thereof.

In the first section, the reinforcement resin may be melted andimpregnated into the matrix resin. Particularly, the temperature of thefirst section (T₁) disposed to be closest to the resin injection partmay be in a range of about (T_(m)−5)° C. to (T_(m)+5)° C. as T_(m) beinga melting temperature of the reinforcement resin. When the temperatureof the first section is lower than the predetermined range, for example,T₁ is less than (T_(m)−5)° C., the tensile modulus of elasticity byimpregnation may deteriorate due to the heat deficiency. When thetemperature of the first section is greater than the predeterminedrange, for example, T₁ is greater than (T_(m)+5)° C., the physicalproperties may deteriorate due to melting of the reinforcement material.Accordingly, it is preferable that the temperature of the first section(T₁) is in a range of about (T_(m)−5)° C. to (T_(m)+5)° C.

After the melting and impregnating of the reinforcement resin into thematrix resin, the method of preparing a thermoplastic resin compositeaccording to an exemplary embodiment of the present invention mayfurther include a step of recrystallizing the melted and impregnatedresin composite in the second section. A temperature of arecrystallization section or the second section (T₂) may be is in arange of about (Tc−5)° C. to (T_(c)+5)° C. as T_(c) represents arecrystallization temperature of the reinforcement resin, or in a rangeof −70° C. from the melting temperature (T_(m)) of the reinforcementresin to −50° C. from T_(m), that is from about (T_(m)−70)° C. to(T_(m)−50)° C. The temperature of the recrystallization section may bedetermined by considering an effect of increased physical properties dueto the crystalline structure of resin which is formed by heat treatmentof resin at the recrystallization temperature after the melting. Afterrecrystallization section, the resin may be cooled to form a shape. Therecrystallization temperature may be measured for example, by Tc of DSC.

Since the temperature of the second section (T₂) is less than that ofthe first section (T₁), the temperature of the second section may belowered by using a cooling apparatus located between the first andsecond sections. For example, a cooling unit of the belt may beinstalled between the first and second sections. In the cooling step,the resin composite may be cooled in a press state after the melting andimpregnating steps, such that shrinkage of a fiber reinforcementmaterial may be prevented. The cooling step can increase dimensionalstability by preventing the reinforcement resin shrinkage and maintainsthe physical properties of the fiber reinforcement resin. The coolingtemperature may be gradually lowered from the temperature of the meltingand impregnating steps to room temperature.

The double belt press laminator may be divided into at least twosections having the different temperature conditions, for example, thedouble belt press laminator may be divided into two, three, four, fiveportions, or the like. In an exemplary embodiment of the presentinvention, when the laminator has at least two sections, each sectionmay be operated separately driven by separate rollers, and thetemperature of each section may be controlled separately.

As shown in FIG. 3, the double belt press laminator may include four ormore sections having the different temperature conditions where thesections may be sequentially divided into a first section, a secondsection, a third section, and a fourth section located from the resininjection part of the laminator to the resin discharge part thereof. Inparticular, a temperature of the second section (T₂) may be in a rangeof about (T_(m)−70)° C. to (T_(m)−50)° C., a temperature of the thirdsection (T₃) may be in a range of about (T_(m)−90)° C. to (T_(m)−80)°C., and a temperature of the fourth section (T₄) may be in a range ofabout (T_(m)−110)° C. to (T_(m)−90)° C.

In an exemplary embodiment of the present invention, the matrix resinand the reinforcement resin may be laminated before the melting andimpregnating steps. In the laminating, the matrix resin and thereinforcement resin may be laminated in consideration of a thickness ofa final product and be inserted into the double belts. The matrix resinand the reinforcement resin may be laminated in various combinationswithout limitation. For example, the matrix resin and the reinforcementresin may be staked in an order of the matrix resin, the reinforcementmaterial and matrix resin.

Preferably, the ratio of an interval between the double belts of thelaminator to a total thickness of laminate stacked with the matrix resinand the reinforcement resin may be of about 0.75 to 0.95. The ratio mayinfluence the physical properties of the resin composite. Since thedecreased belt interval may increase the lamination pressure, thetensile stiffness of the resin composite may be increased. This changein the physical properties may be caused by increased impregnation ratedue to the elevated pressure and by decreased air gap (increasedspecific gravity). When the ratio is less than the predetermined range,for example, less than about 0.75, the materials may not be uniformlylaminated/compressed, such that a product may have non-even thicknessand bad appearance. Meanwhile, a roll gap is greater than thepredetermined range, for example, greater than about 0.95, the tensilemodulus of elasticity may be excessively decreased.

In the method of preparing the thermoplastic resin composite accordingto the present invention, the retention time of the resin in thelaminator may be affected by various conditions, and thus may besuitably selected.

The thermoplastic resin composite as described above or manufacturedaccording to exemplary methods of the present invention may haveimproved tensile properties and specific gravity of about 0.880 to0.900, tensile strength of about 0.80 to 1.10, and tensile modulus ofabout 0.80 to 1.1.

The present invention provides the resin composite may the matrix andthe reinforcement material which are selected from the thermoplasticresins, and the method of preparing the same to achieve the highproductivity in the continuous process. The resin composite havingsubstantially physical properties may be prepared by controlling processconditions such as a temperature, a pressure and the like. In addition,the resin composite may be widely used in various fields, for example,civil engineering and architectural fields, a transportation field suchas vehicle materials, or the like, electronic and electric devicefields, aviation and aerospace fields and the like.

EXAMPLE

The present invention will be described in more detail through thefollowing Examples, but the scope of the present invention is notlimited to the following Examples.

Example 1: Preparation of Resin Composite

In order to prepare a resin composite, a reinforcement resin fiber and amatrix resin were prepared. Specifically, a homopolypropylene resin (FR150, Lotte Chemical, MI: 10, T_(m): 166° C., Mw: 230,000) was used asthe reinforcement resin. A grey yarn was prepared by using thereinforcement resin and was weaved to for a fabric obtained by 1:1 plainweaving the fiber was used. A propylene/ethylene copolymer resin (MI:25, T_(m): 130° C.) was manufactured in a film form and used as thematrix resin.

In order to stack three layers which was sequentially composed of afiber reinforcement material/a matrix/the fiber reinforcement material,the reinforcement resin and the matrix resin were mounted on a rollshaped unwinder, and sequentially laminated while being transported fromthe unwinder, such that the laminator of reinforcement resin and thematrix resin were inserted into a double belt press laminator. Thesimple stacked sample before being processing had a thickness of 0.56mm, and the double belt laminator was operated at a belt speed of 8mm/sec and a retention time of 150 seconds with a belt interval (rollgap) of 0.5 mm. The double belt press laminator included four dividedsections, and a schematic view specifically indicating four sections ofthe double belt press is illustrated in FIG. 3. In the presentExperiment, the four sections had the same belt temperature of T_(m)−5°C., and a belt interval of 0.5 mm.

As physical properties of a self-reinforced composite prepared by themethod, specific gravity was measured according to ISO-1183, and tensilestrength and tensile modulus of elasticity were measured according toISO-527.

As a result, the obtained self-reinforced composite had specific gravityof 0.874, tensile strength of 0.88, and tensile modulus of 0.30.

Example 2: Evaluation of Effect of Lamination Temperature

As Example 1, a reinforcement resin and a matrix resin were prepared anda resin composite was prepared using a double belt laminator, except forthe temperature of double belts laminator. That is, the belt temperaturein first to fourth sections of double belt were equally set as fourtemperatures, such as (T_(m)−10)° C., (T_(m)−5)° C., T_(m), and(T_(m)+5)° C. of a fiber reinforcement material, the melting temperaturefor Experiments 1 to 4.

Specific gravity, tensile strength and tensile modulus of theself-reinforced composite prepared by the method were measured by thesame method as Example 1, and the results were illustrated in thefollowing Table 1 and FIG. 4. FIG. 4 is a graph illustrating the changesin physical properties depending on a double belt laminationtemperature.

TABLE 1 Classification Experiment 1 Experiment 2 Experiment 3 Experiment4 Temperature (° C.) (T_(m)−10) ° C. (T_(m)−5) ° C. (T_(m)+0) ° C.(T_(m)+5) ° C. of four sections Specific Gravity 0.869 0.874 0.891 0.897Tensile Strength 0.92 0.88 0.84 0.61 Tensile Modulus 0.33 0.30 0.66 1.02

As illustrated in Table 1 and FIG. 4, in the case of increasing aprocessing temperature in a double belt press lamination process,tensile modulus of the obtained resin composite was increased, buttensile strength was decreased. The increased stiffness of the resincomposite may be caused by increased impregnation rate and decreased airgap. In addition, the decreased tensile strength may be caused bydecreased physical properties of the reinforcement material itself bymelting of the reinforcement fiber. Therefore, by cooling the resincomposite after applying heat to the melting of reinforcement material,the strength and stiffness must be maintained, with preventingdeterioration of the physical properties of the reinforcement resin.

Example 3: Effect of Lamination Pressure

As Example 1, a reinforcement resin and a matrix resin were prepared anda resin composite was prepared using a double belt laminator, except forthe ratio of roll gap of double-belt laminator to the stacked resins.That is, the ratio of roll gap of double-belt laminator to the stackedresins was set to 0.71 (0.4 mm roll gap), 0.89 (0.5 mm roll gap), or1.07 (0.6 mm roll gap).

Specific gravity, tensile strength and tensile modulus of theself-reinforced composite prepared by the method were measured by thesame method as Example 1, and the results were illustrated in Table 2.In the appearance evaluation in the following Table 2, when thearrangement of the woven fiber was not deformed and the thickness changeand the fiber arrangement defect due to bending or folding in theprocessing, the appearance was evaluated as the term “good” state.

TABLE 2 Classification Experiment 5 Experiment 6 Experiment 7 Roll Gap(mm) 0.71 0.89 1.07 Specific Gravity 0.885 0.874 0.869 Tensile Strength1.17 0.88 0.65 Tensile Modulus 0.70 0.30 0.14 Appearance Wrinkle PatternGood Good (Defective)

The present Example was performed to test a change in physicalproperties of the obtained resin composite depending on an increasedlamination pressure. When the decreased belt interval was set toincrease the lamination pressure, tensile stiffness of the obtainedresin composite was increased. This change in the physical propertieswas caused by improved impregnation rate due to the pressure increaseand air gap decrease, in other words, due to an increase in specificgravity. When the ratio of roll gap to the thickness of stackedmaterials was 0.71, the materials were not uniformly laminated and/orcompressed, such that a thickness of a product was not uniform, and theappearance was not good. Therefore, it is preferable that the ratio ofthe roll gap to the thickness of stacked materials is 75% or greater. Inthe case in which the ratio of roll gap to the thickness of stackedmaterials was 1.07, tensile modulus of elasticity was excessivelydecreased.

Example 4: Effect of Retention Time of Resin in Belt

As Example 1, a reinforcement resin and a matrix resin were prepared anda resin composite was prepared using a double belt laminator, except fora retention time of the resin in a belt. That is, a retention time ofthe resin in a belt was set to 150 seconds and 470 seconds.

Specific gravity, tensile strength and tensile modulus of elasticity forthe self-reinforced composite prepared by the method were measured bythe same method as Example 1, and the results were illustrated in thefollowing Table 3. When the woven state of the fiber reinforcement resinand the constant pattern were maintained after a double belt laminationprocess, the state was determined as good state. When the startingmaterials were overlapped or melted, so as to generating wrinkles, thestate was determined as bad state.

Specific gravity, tensile strength and tensile modulus of the resincomposite were measured, and the experimental results were illustratedin the following Table 3.

TABLE 3 Classification Example 1 Experiment 8 Retention Time 150 sec 470sec Specific Gravity 0.874 0.895 Tensile Strength 0.90 0.74 TensileModulus 0.30 1.13

In the case of increasing the retention time in the belt in a laminationprocess using a double belt press, tensile stiffness of the obtainedresin composite was increased, but tensile strength thereof wasdecreased. These changes in the physical properties of the resincomposite were caused by an increased energy amount applied on thesample. When the retention time was excessively short, the processingenergy was not sufficiently transferred, so as to deteriorate thephysical properties of resin composite. When the retention time wasexcessively long, the tensile strength of the reinforcement material wasdecreased due to shrinkage and melting by heat.

Example 5: Effect of Cooling Process (Recrystallization Section)

As Example 1, a reinforcement resin and a matrix resin were prepared anda resin composite was prepared using a double belt laminator, exceptthat the temperature in each section of FIG. 3 was set differently asExperiments 9 to 12.

The temperatures of four sections were equally set in Experiment 9. InExperiments 10 to 12, the temperatures of the first to fourth sectionswere differently set with the temperature gradient being from thehighest temperature at the closest section to the resin injection partof the laminator to the lowest temperature at the closest section to theresin discharge part. In addition, a retention time in each section wasequally set. The temperature conditions in Experiments 9-12 weresummarized in the following Table 4.

TABLE 4 Classi- Experiment Experiment Experiment Experiment fication 910 11 12 1st Section Tm +0 Tm −5 Tm +0 Tm +5 (° C.) 2nd Section Tm +0 Tm−65 Tm −65 Tm −65 (° C.) 3rd Section Tm +0 Tm −85 Tm −85 Tm −85 (° C.)4th Section Tm +0 Tm −100 Tm −100 Tm −100 (° C.)

Specific gravity, tensile strength and tensile modulus of theself-reinforced composite as Example 1, and the results were illustratedin Table 5.

TABLE 5 Classi- Experiment Experiment Experiment Experiment fication 910 11 12 Specific 0.891 0.880 0.887 0.896 Gravity Tensile 0.84 1.00 1.071.00 Strength Tensile 0.66 0.83 0.91 1.00 Modulus

In the case of performing a cooling process in the second to fourthsections after a heating process in the first section in FIG. 3, whenthe temperature of the first section (T₁) was increased to T_(m)±5° C.,both of the tensile stiffness and tensile strength of the resincomposite were increased. The causes of the physical properties changesof the resin composite was due to an increased melting and impregnationproperty of the matrix resin and/or reinforcement resin to the resincomposite by increasing the temperature of the first section (T₁). Inaddition, the additional melting and the decreased physical propertiesof reinforcement resin was prevented by cooling the material under thepressured state and the recrystallization of the composite.

In Comparison of the results of Table 5 with those of Table 1, when thecomposite was prepared at the same temperature in all four sections, thehigher melting temperature increased the specific gravity and tensilemodulus of elasticity, but lowered the tensile strength. However,referring to Experiments 10 to 12 of Table 5, the higher meltingtemperature in the first section increased the specific gravity andtensile modulus, with maintaining the tensile strength. Specifically, inExperiment 2 of Table 1, the tensile strength was decreased and tensilemodulus of elasticity was also excessively low (e.g. 0.30) at atemperature of (T_(m)−5)° C. in the first section. However, inExperiment 10 of Table 5, both of the tensile strength and tensilemodulus of elasticity were excellent.

FIG. 5 is a graph showing changes in physical properties of an exemplaryresin composite obtained by applying the recrystallization process in anexemplary embodiment of the present invention. The crystalline changesin the recrystallization section were summarized in the following Table6 or FIGS. 6-8, which illustrated the changes in half width at variousinitial temperatures at the first section.

TABLE 6 Experiment Experiment Experiment Experiment Half Width 8 9 10 116.9° 0.57 0.537 0.424 0.411 8.4° 0.545 0.537 0.455 0.447 9.1° 0.5930.553 0.442 0.428 10.4°  0.473 0.603 0.215 0.395 10.8°  0.86 0.88 0.5810.487

FIG. 6 is a DSC graph showing the melting point change of the obtainedresin composite. With respect to the starting materials of the compositebefore processing, the crystallinity and the melting temperatureincreased due to the heating and cooling treatment under the pressure,as the initial melting temperature increased.

FIG. 7 illustrates the crystalline structures of the obtained resincomposite. According to XRD graph of FIG. 8, as the initial meltingtemperature from the first section was increased before applying coolingunder the pressure state, a XRD pattern approached to an alpha form,which is the most stable crystalline structure among crystallinestructures of the resin illustrated in FIG. 7, and a half width wasdecreased. The decreased half width may indicate an increasedcrystallinity. In view of the results, as the initial meltingtemperature increased before applying cooling step under the pressurestate, the tensile modulus of the composite increased. When thetemperatures of all sections were equal, or when the temperature of thefirst section was lower than Tm−5° C., tensile modulus was decreased bythe decreased impregnation due to a deficiency of heat. When thetemperature of the first section was higher than Tm+5° C., the physicalproperties were deteriorated by the melting of the reinforcementmaterial. Therefore, the temperature of the first section (T₁) may bepreferably in a range of about (T_(m)−5)° C. to (T_(m)+5)° C.

What is claimed is:
 1. A resin plastic composite, which is manufacturedby a method comprising melting a reinforcement resin and a matrix resin;and impregnating the reinforcement resin into the matrix resin to formthe resin composite, wherein the resin composite is prepared using adouble belt press laminator comprises four or more sections havingdifferent temperature conditions where a first section is closest to theresin injection part of the laminator and a second section, a third anda fourth sections are located sequentially from the first section to theresin discharge part, wherein a temperature in the double belt presslaminator decreases from the resin injection part to a resin dischargepart of the laminator, and a temperature of the first section (T₁) is ina range of about (T_(m)−5) ° C. to (T_(m)+5) ° C., a temperature of thesecond section (T₂) is in a range of about (T_(m)−70) ° C. to (T_(m)−50)° C., a temperature of the third section (T₃) is in a range of about(T_(m)−90) ° C. to (T_(m)−80) ° C., and a temperature of the fourthsection (T₄) is in a range of about (T_(m)−110) ° C. to (T_(m)−90) ° C.,as Tm being a melting temperature of the reinforcement resin, wherein aratio of an interval between the double belts of laminator to athickness of the laminated matrix resin and the reinforcement resinranges from about 0.75 to about 0.95, and wherein the resin compositehas specific gravity of about 0.880 to 0.900, a tensile modulus of about0.80 to 1.1 Gpa, and a tensile strength of about 0.80 to 1.10 Mpa. 2.The resin plastic composite of claim 1, which is prepared in continuousprocess.
 3. The resin plastic composite of claim 1, wherein the methodfurther comprises recrystallizing the formed resin composite in thesecond section.
 4. The resin plastic composite of claim 1, wherein thetemperature of the second section (T₂) is lowered by using a coolingapparatus positioned between the first and second sections.
 5. The resinplastic composite of claim 4, wherein a cooling apparatus is installedbetween the first and second sections.
 6. The resin plastic composite ofclaim 1, wherein the method further comprises laminating the matrixresin and the reinforcement resin before melting the reinforcementresin.
 7. The resin plastic composite of claim 1, wherein the matrixresin is in a form of a film, and the reinforcement resin is in a formof a fiber or fabric.
 8. The resin plastic composite of claim 1, whereinthe matrix resin and the reinforcement resin have a melting temperatureof about 130 to 165° C.
 9. The resin plastic composite of claim 1,wherein the matrix resin and the reinforcement resin are each athermoplastic resin comprising at least one selected from the groupconsisting of polyethylene, polypropylene, anacrylonitrile-butadiene-styrene (ABS) resin, polycarbonate, polyacetal,polyamide, polystyrene, and polyphenylene sulfide.
 10. The resin plasticcomposite of claim 1, wherein the matrix resin and the reinforcementresin are polyolefin resin.
 11. The resin plastic composite of claim 1,wherein each the first and second section of the laminator is driven bya separate roller.
 12. The resin plastic composite of claim 6, whereineach section of the laminator is driven by a separate roller.